EP1306305B1 - Procédé et système de maintenance d'aéronefs - Google Patents

Procédé et système de maintenance d'aéronefs Download PDF

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Publication number
EP1306305B1
EP1306305B1 EP02023950A EP02023950A EP1306305B1 EP 1306305 B1 EP1306305 B1 EP 1306305B1 EP 02023950 A EP02023950 A EP 02023950A EP 02023950 A EP02023950 A EP 02023950A EP 1306305 B1 EP1306305 B1 EP 1306305B1
Authority
EP
European Patent Office
Prior art keywords
aircraft
maintenance
sensor device
sensor
signals
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP02023950A
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German (de)
English (en)
Other versions
EP1306305A2 (fr
EP1306305A3 (fr
Inventor
Jürgen Halm
Kurt-Volker Hechtenberg
Werner Kolander
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
EADS Deutschland GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH, EADS Deutschland GmbH filed Critical Airbus Operations GmbH
Publication of EP1306305A2 publication Critical patent/EP1306305A2/fr
Publication of EP1306305A3 publication Critical patent/EP1306305A3/fr
Application granted granted Critical
Publication of EP1306305B1 publication Critical patent/EP1306305B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
    • G07C5/0841—Registering performance data
    • G07C5/085—Registering performance data using electronic data carriers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60C—VEHICLE TYRES; TYRE INFLATION; TYRE CHANGING; CONNECTING VALVES TO INFLATABLE ELASTIC BODIES IN GENERAL; DEVICES OR ARRANGEMENTS RELATED TO TYRES
    • B60C23/00—Devices for measuring, signalling, controlling, or distributing tyre pressure or temperature, specially adapted for mounting on vehicles; Arrangement of tyre inflating devices on vehicles, e.g. of pumps or of tanks; Tyre cooling arrangements
    • B60C23/02—Signalling devices actuated by tyre pressure
    • B60C23/04—Signalling devices actuated by tyre pressure mounted on the wheel or tyre
    • B60C23/0408—Signalling devices actuated by tyre pressure mounted on the wheel or tyre transmitting the signals by non-mechanical means from the wheel or tyre to a vehicle body mounted receiver
    • B60C23/0479—Communicating with external units being not part of the vehicle, e.g. tools for diagnostic, mobile phones, electronic keys or service stations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C3/00—Registering or indicating the condition or the working of machines or other apparatus, other than vehicles
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/006—Indicating maintenance
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/008—Registering or indicating the working of vehicles communicating information to a remotely located station

Definitions

  • the invention relates to a diagnostic system and a diagnostic method for supporting aircraft maintenance.
  • monitoring of a machine comprises a controller and an interface device between which there is an infrared, radio or wire connection.
  • One or more ports receive signals from transducers on the machine. The signals are processed and can be stored in Save. The processed signals are transmitted from an interface port to a controller port.
  • Out US 2001/0008083 is the monitoring of the tire condition of a vehicle known.
  • at least one tire parameter is detected by measuring the rotational angle of the tire or wheel.
  • the measured position is transmitted from the wheel or tire to a receiver in the vehicle.
  • the invention is therefore based on the object to support the maintenance of a commercial aircraft to realize a fast and reliable location of errors and a corresponding provision of information for maintenance personnel with the least possible effort and thus to achieve a reduction in the repair time.
  • Fig. 1 is a schematic representation of a located on the ground airliner 1 visible.
  • a so-called "walk around" check must be completed, ie a mechanic checks the functionality of important systems.
  • a circumnavigation of the entire aircraft is necessary and important aircraft systems and aircraft components are checked, for example, checks on the nose wheel 3A and wheel gears 3B polling the air pressure and a check of the brakes.
  • flap systems 4 and 4 ' such as spoilers and landing flaps and necessary for the adjustment hydraulic actuators - exemplified with 5.
  • a mechanic commissioned with the ground check receives a handset 6 as part of a diagnostic system 2 as work equipment, which on the one hand displays the maintenance information (check list with points to be processed) required for a specific maintenance task on a display 7 and interrogates diagnostic information of maintenance-intensive aircraft systems can.
  • the maintenance information can be provided comprehensively on the handset 6, preferably by means of an exchangeable storage medium.
  • a connection of the handset 6 is provided to a stationary unit, such as a personal computer or a server, wherein the connection via a suitable interface, which is to be selected according to the amount of data to be transmitted.
  • sensor devices 8 are provided on the aircraft systems to be serviced. For example, sensors are provided on the hydraulic actuators 5 and 5 'in order to be able to detect actuator defects. The sensor information is queried during a ground check, evaluated and a fault diagnosis (locally determined actuator in order or faulty) is displayed on the display 7 of the handset 6. An embodiment for the diagnosis of actuators is closer in the Fig. 2 described.
  • the sensor devices 8 can also be provided to query the water concentration, the particle concentration or the level in hydraulic systems or in the fuel. Embodiments of this kind are in the FIGS. 3 and 4 specified.
  • the corresponding sensor signals are sent via transmitting devices to a processing unit 9 and processed there and provided on a display unit 10 as information for the mechanic.
  • the processing unit 9 wirelessly receives a receiver 11 Sensor signals. Processing of the information can be done by means of conventional stationary computers or in a preferred embodiment directly by means of pocket PC's or laptops and made available to the mechanic.
  • the handset 6 as working means for the mechanic for this in addition to the display device 10 also includes the processing unit 9 and thus he can make immediate and on-site review of the aircraft components and a fault diagnosis.
  • a signal transmission from the sensor device 8 to the processing unit 9 is wireless over a larger area, approximately over a distance of at least 12 m, is possible.
  • a remote retrieval of information especially in large-capacity aircraft, for example, even access to certain flaps, actuators and the wings due to the large dimensions without aids does not work, achieved with great reliability.
  • Signal transmission is possible for example with radio links or infrared signals.
  • the energy required for signal generation and signal transmission is made available in the area of the sensor devices 8.
  • the sensor devices 8 are preferably designed as energy-independent as possible without intervention in existing aircraft systems. This ensures that an integration of the sensor devices 8 in the aircraft does not affect the functionality of the existing aircraft systems and no additional connection to the power supply of the aircraft is necessary.
  • the power supply of the sensor devices 8 can be provided for example via separate energy sources or energy storage. Preferably, energy generators are to be used which gain energy from the environment, such as from vibration. Shown is this self-powered diagnostic sensors with the possibility of an active wireless query 80 in Fig. 1A ,
  • the sensor device 8 comprises a transmitter / receiver unit (receiver / transmitter) 81, a sensor 82 and a microcontroller (C, signal converter A / DC, Time) 83 for detecting the data and, for example, the time. If an interrogation signal is triggered on the handset 6, the transmission of data to the transceiver unit takes place (Receiver / Transmitter) 11 of the handset 6.
  • the processing unit 9 with the display device (Display and Control) and with a microprocessor-based interface (Controlled Interface) and can perform at least some of the following functions: View work progress, wireless sensor devices query, register and display data, exchange data and instructions, and / or display visualized repair instructions.
  • a passive wireless query 84 can be made by the handset 6. Here the sensors do not need their own energy.
  • a sensor is identified at a shorter distance, for example ⁇ 0.1 m, starting from a transceiver 85 and an HF (rf [radio-frequency]) transponder 86 is activated, a sensor interrogation is carried out and this measured value is transmitted to the transceiver 85 ,
  • a measurement of air pressure in tires can be measured and transmitted using this method.
  • the required energy is taken from the transmission power here.
  • a further embodiment of the invention utilizes sensor devices as diagnostic sensors, which provide active storage of the measured value. The energy required for this can be very low.
  • the retrieval of the memory value is performed with said passive wireless interrogation 84, wherein the required energy is provided from the transmission power of the transceiver 85.
  • optical transponders which enable optical active or passive queries.
  • Fig. 2 an embodiment of the diagnostic system in the range of adjusting devices for flap systems 4, 4 'on the wings of the airliner 1 is shown.
  • a variety of actuators 5 are necessary for the adjustment of the wing flaps and wear of the actuators must be checked regularly. Wear of the spoiler actuators 5 can, for example, cause the entire aircraft in individual flight phases is vibrated by control vibrations (called slipping effect). At the bottom of this error is then usually no longer reproducible and one Accurate determination of the defective actuators can be carried out with the aid of the sensor device 8A arranged on the corresponding actuator 5, which has recorded and optionally processed and stored measurement data during the flight.
  • a preprocessing of the sensor signal within a preprocessing module of the sensor device 8 may be advantageous in order to achieve a data reduction.
  • Fig. 3 an embodiment of the diagnostic system 2 in the area of a hydraulic system for adjusting devices in the commercial aircraft 1 is shown.
  • a hydraulic tank 12 which is arranged in the embodiment shown in the region of the landing gear shaft 13 of the aircraft 1, the water content of the hydraulic fluid is regularly to determine, because by water entry, the life of hydraulic fluid is considerably shortened. A high water content leads to damage to the entire hydraulic system.
  • the sensor device 8B is arranged for this application for measuring the concentration of water in the hydraulic tank at the bottom of the container 12.
  • the mechanic who is to carry out a state diagnosis of the hydraulic fluid can read the diagnostic information, for example the water content, on the display 7. He does not have to get in through the access flap in the landing gear shaft and make 12 measurements directly on the hydraulic tank.
  • Fig. 4 an embodiment of the diagnostic system 2 in the area of a fuel tank 14 in the airliner 1 is shown. Water deposits in the fuel tank 14 must be removed regularly.
  • a water drainage valve 15 is provided. In proximity to this valve 15, a fuel water detection sensor 8C is disposed within the tank 14.
  • the sensor device 8C which can measure the amount of water in the tank or the water level of the settled amount of water and transmitted to the processing unit 9, the maintenance personnel can be informed of the water level via the display device 10 (display 7).
  • the time for a necessary drainage is thus relatively accurately determined and the necessary work need only be carried out as needed.
  • the transmission of the measurement signals from the sensor device 8C to the processing unit 9 is also wireless here.
  • the signal is transmitted from the fuel water detection sensor 8C to the processing unit 9 and by means of evaluation software, the measured value is processed and processed as diagnostic information.
  • the mechanic is also informed, depending on the evaluation software, whether water drainage is necessary.
  • Such maintenance information can depending on the application of the diagnostic system comprising the handset 6, preferably provided by an exchangeable storage medium.
  • Fig. 5 an example of a flowchart is shown with the representation of a diagnostic query.
  • Sensor signals are present at a sensor device 8 and can be retrieved by a correspondingly addressed request from the handset 6 from. If a query was unsuccessful and no response has been received within a certain time, for example 10ms, the query is retried. The sensor signals are transmitted to the processing unit 9, processed, the result stored and displayed as needed. After completion of the query, a new query of a next diagnostic sensor can be performed.
  • the present invention is not limited to the aforementioned embodiments, but the use of the invention for a sensor-based maintenance support on many aircraft components or aircraft systems is possible.
  • Maintenance-intensive system components i. Components that must be checked frequently due to frequent failure or safety relevance can be equipped with the present invention or checked, which significantly reduces the maintenance of these components.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Arrangements For Transmission Of Measured Signals (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)
  • Vehicle Cleaning, Maintenance, Repair, Refitting, And Outriggers (AREA)
  • Testing Electric Properties And Detecting Electric Faults (AREA)

Claims (18)

  1. Système de diagnostic pour la maintenance d'avions destiné à faciliter la maintenance d'un avion de ligne, comportant
    un dispositif de détection (8) qui produit et mémorise des signaux de capteurs relatifs à des systèmes ou composants d'avion nécessitant beaucoup de maintenance (5, 5' ; 12 ; 14) à un point de contrôle pendant le vol ou le temps passé au sol,
    une alimentation en énergie pour le dispositif de détection (8), laquelle est indépendante d'un réseau de bord d'avion,
    une unité de traitement (9) destinée à la mise en oeuvre d'un traitement de signaux, une liaison sans fil disponible pendant le temps que l'avion passe au sol entre le dispositif de détection (8) et l'unité de traitement (9) pour la transmission des signaux de capteurs et
    un dispositif d'affichage (10) sur lequel sont transmis des signaux de capteurs ou des signaux d'analyse sélectionnés et sur lequel sont affichées les informations de diagnostic ainsi que, le cas échéant, des informations de maintenance requises pour une intervention de maintenance.
  2. Système de diagnostic pour la maintenance d'avions selon la revendication 1,
    caractérisé en ce que le dispositif de détection (8) présente un module de traitement destiné au traitement préliminaire des signaux de capteurs à l'intérieur du dispositif de détection (8), les signaux de capteurs étant traités à l'intérieur du module de traitement et transformés en signaux d'analyse ou intermédiaires.
  3. Système de diagnostic pour la maintenance d'avions selon la revendication 2,
    caractérisé en ce que le dispositif de détection (8) est équipé d'un générateur d'énergie et/ou d'un accumulateur d'énergie.
  4. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 3,
    caractérisé en ce que le dispositif de détection (8) présente un transpondeur HF (84) pour l'interrogation passive sans fil de signaux de capteurs.
  5. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 3 ou 4,
    caractérisé en ce que le dispositif de détection (8) présente un dispositif de stockage actif pour la mémorisation d'un signal de capteur ainsi qu'un transpondeur (84) pour l'interrogation passive sans fil de signaux de capteurs.
  6. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 5,
    caractérisé en ce que le dispositif de détection (8) présente au moins un transpondeur optique pour l'interrogation optique active ou passive.
  7. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 4 à 6,
    caractérisé en ce que la transmission des signaux de capteurs est prévue au moyen de dispositifs radio ou infrarouge.
  8. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 7,
    caractérisé en ce que l'unité de traitement (9) comporte des moyens d'analyse des signaux de capteurs afin de réaliser un diagnostic de panne.
  9. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 8,
    caractérisé en ce que l'unité de traitement (9) présente un support de mémoire afin de stocker des informations de diagnostic ainsi que des informations de maintenance requises pour une intervention de maintenance.
  10. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 9,
    caractérisé en ce qu'un dispositif d'affichage (10) présente un écran (7) pour l'affichage d'informations de diagnostic ainsi que d'informations de maintenance requises pour une intervention de maintenance.
  11. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 10,
    caractérisé en ce que l'unité de traitement (9) ainsi que le dispositif d'affichage (10) sont réunis dans un appareil portatif (6).
  12. Système de diagnostic pour la maintenance d'avions selon la revendication 11,
    caractérisé en ce que l'appareil portatif (8) peut être raccordé à un poste d'ordinateur fixe, par exemple un calculateur individuel et/ou un serveur.
  13. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 12,
    caractérisé en ce que le dispositif de détection (8, 8A) est prévu sur des actionneurs hydrauliques (5, 6') de volets d'ailes (4, 4') afin de déterminer l'usure des actionneurs.
  14. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 13,
    caractérisé en ce que le dispositif de détection (8, 8B) est prévu dans la partie inférieure du réservoir hydraulique (12) afin de déterminer la teneur en eau et/ou la concentration en particules.
  15. Système de diagnostic pour la maintenance d'avions selon l'une des revendications 1 à 14,
    caractérisé en ce que le dispositif de détection (8, 8C) est prévu dans le réservoir d'avion (14) dans la zone de la vanne de drainage d'eau (15) afin de déterminer la concentration en eau.
  16. Procédé de diagnostic pour la maintenance d'avions destiné à faciliter la maintenance d'un avion de ligne, comportant les étapes suivantes :
    au niveau de systèmes ou composants d'avion nécessitant beaucoup de maintenance (5, 5' ; 12 ; 14), des signaux de capteurs sont produits et
    mémorisés sur un lieu de contrôle dans un dispositif de détection (8) pendant le vol ou le temps au sol,
    le dispositif de détection (8) est alimenté en énergie indépendamment d'un réseau de bord d'avion,
    pendant le temps que l'avion passe au sol, les signaux de capteurs sont transmis sans fil du dispositif de détection (8) à une unité de traitement (9),
    un traitement des signaux s'effectue dans l'unité de traitement (9),
    des signaux de capteurs ou des signaux d'analyse sélectionnés sont transmis à un dispositif d'affichage (10) et
    ces informations de diagnostic ainsi que, le cas échéant, des informations de maintenance requises pour une intervention de maintenance, sont affichées sur le dispositif d'affichage (10).
  17. Procédé de diagnostic pour la maintenance d'avions selon la revendication 16,
    caractérisé en ce que les signaux de capteurs sont soumis à un traitement préliminaire à l'intérieur du dispositif de détection (8) afin d'obtenir une réduction des données et en ce que des signaux d'analyse ou intermédiaires sont transmis à l'unité de traitement (9).
  18. Procédé de diagnostic pour la maintenance d'avions selon l'une des revendications 16 à 17,
    caractérisé en ce que les signaux (signaux de capteurs ou signaux intermédiaires ayant déjà subi un traitement préliminaire) transmis à l'unité de traitement (9) sont traités en fonction de l'intervention de maintenance requise.
EP02023950A 2001-10-27 2002-10-25 Procédé et système de maintenance d'aéronefs Expired - Lifetime EP1306305B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10153151A DE10153151A1 (de) 2001-10-27 2001-10-27 Diagnosesystem sowie Diagnoseverfahren zur Unterstützung der Flugzeugwartung
DE10153151 2001-10-27

Publications (3)

Publication Number Publication Date
EP1306305A2 EP1306305A2 (fr) 2003-05-02
EP1306305A3 EP1306305A3 (fr) 2006-01-04
EP1306305B1 true EP1306305B1 (fr) 2009-05-27

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EP02023950A Expired - Lifetime EP1306305B1 (fr) 2001-10-27 2002-10-25 Procédé et système de maintenance d'aéronefs

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US (2) US7050894B2 (fr)
EP (1) EP1306305B1 (fr)
AT (1) ATE432217T1 (fr)
DE (2) DE10153151A1 (fr)

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EP1306305A2 (fr) 2003-05-02
EP1306305A3 (fr) 2006-01-04
ATE432217T1 (de) 2009-06-15
DE50213572D1 (de) 2009-07-09
US20030083794A1 (en) 2003-05-01
US20040162651A1 (en) 2004-08-19
US7050894B2 (en) 2006-05-23
DE10153151A1 (de) 2003-05-15

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